ITU-R S 1593-2002 Methodology for frequency sharing between certain types of homogeneous highly-elliptical orbit non-geostationary fixed-satellite service systems in the 4 6 GHz an.pdf

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1、 Rec. ITU-R S.1593 1 RECOMMENDATION ITU-R S.1593 Methodology for frequency sharing between certain types of homogeneous highly-elliptical orbit non-geostationary fixed-satellite service systems in the 4/6 GHz and 11/14 GHz frequency bands (Question ITU-R 231/4) (2002) The ITU Radiocommunication Asse

2、mbly, considering a) that many fixed-satellite service (FSS) frequency bands may be used for both geostationary (GSO) and non-GSO satellite networks according to the Radio Regulations; b) that the technology advances necessary to allow the implementation of non-GSO FSS satellite systems capable of p

3、roviding regional or worldwide service to small earth stations in a cost-effective manner are becoming available; c) that some non-GSO FSS systems are not designed to employ the interference mitigation technique of satellite diversity; d) that studies have shown that without the use of interference

4、mitigation techniques, it will be impracticable for large numbers of non-GSO FSS systems to share the same frequency band when the systems are of significantly varying design; e) that studies have shown that multiple non-GSO FSS systems using only the mitigation technique of homogeneous design can s

5、hare with each other in the same frequency bands; f) that for non-GSO FSS systems using a highly-elliptical orbit (HEO) design, the implementation of satellite diversity comes at a design cost and complexity that may make its use by such systems in sharing with other types of non-GSO FSS systems dif

6、ficult; g) that multiple non-GSO FSS systems that operate in the 11/14 GHz and 4/6 GHz bands using an HEO design (e.g. USAKUS2 as described in Recommendation ITU-R S.1328) can employ geometric mitigation techniques to share with each other by several methods of satellite separation, including interl

7、eaving of satellites within orbital planes, recommends 1 that in the 4/6 GHz and 11/14 GHz bands, the methodology presented in Annex 1 be used to perform analysis of frequency sharing between co-frequency, co-directional non-GSO FSS satellite systems of homogeneous sub-geosynchronous HEO design, i.e

8、. the apogees, perigees, and inclinations of the systems are identical. NOTE 1 The methodology in Annex 1 may also be applicable to other types of non-GSO FSS systems. To determine whether the sharing prospects are different between multiple homogeneous non-GSO FSS systems of the type considered in

9、Annex 1 and inhomogeneous non-GSO FSS systems, further study is required. 2 Rec. ITU-R S.1593 ANNEX 1 Methodology for sharing between certain types of homogeneous HEO non-GSO FSS systems in the 4/6 GHz and 11/14 GHz frequency bands 1 Introduction The methodology presented in this Annex addresses sha

10、ring between certain types of homogeneous non-GSO FSS systems in the 4/6 GHz and 11/14 GHz frequency bands. This approach applies to systems that have homogeneous orbits; i.e. the apogee, perigee, and inclination are identical. The systems must have exactly the same ground tracks for the active port

11、ions of their orbits. The difference will come in the phasing of the satellites in the orbital track. The methodology applies to systems that are designed such that the portions of the orbit in which the satellites are either transmitting or receiving (active arcs) do not cross each other. The appro

12、ach involves the interleaving of satellites within the same orbital ground track when sharing between multiple non-GSO FSS systems. It is applicable generally to non-GSO systems that employ HEO in which the satellites are only transmitting or receiving in a certain portion of the orbit. However, it

13、may be applicable to other non-GSO systems provided that the active portions of the orbit do not cross each other. This approach eliminates in-line interference events since the active arcs do not cross. This means that there will be no need for complicated switching strategies in order to avoid in-

14、line interference events and there will be no need to know the exact locations of the satellites in other constellations as they will be phased in such a way that there will always be a minimum separation between two satellites in adjacent systems. Appendix 1 to this Annex contains an example appli-

15、cation of this methodology. 2 Description of methodology The following Steps comprise this methodology: Step 1: Select a minimum true anomaly separation angle between satellites in adjacent constellations. This is the satellite separation angle between adjacent satellites in two constellations near

16、apogee, when the satellites in adjacent constellations will be the closest to each other. At other locations in the active arc (or during any other portion of the orbit), satellites in adjacent systems will be further separated. The approach taken here is to select a minimum true anomaly separation

17、angle between two satellites that are in adjacent constellations around the apogee. Since the apogee point is when the satellites are travelling at the slowest rate of speed, if the satellites in adjacent constellations are placed symmetrically around the apogee, this will be when the satellites wou

18、ld be closest to each other. Thus, the apogee will be chosen as the centre true anomaly and the true anomalies of the satellites in the two constellations will be equal to the true anomaly at apogee plus one-half the minimum true anomaly separation angle and the true anomaly at apogee minus one-half

19、 the minimum true anomaly separation angle. The resultant true anomalies (E) for the two satellites are given in equations (1) and (2): 2)(1angleSeparationapogeeEE += degrees (1) Rec. ITU-R S.1593 3 2)(2angleSeparationapogeeEE = degrees (2) Step 2: Determine the orbital locations (latitude, longitud

20、e and altitude) of the satellites that are located at the minimum true anomaly separation. From the values for the true anomalies and the other orbital parameters for the system, it is then possible to calculate the eccentric anomaly (Ee), mean anomaly (Em) and time (t) (relative to the time of the

21、ascending node). From these values, it is possible to calculate the latitude, longitude and orbital altitude of the two satellites. The relevant equations for these calculations are as follows: +=eeEEe112tantan21degrees (3) where e is the eccentricity of the orbit. eemEeEE sin= degrees*(4) ()amamtEE

22、Tt +=360s (5) where: T : period of the orbit Ema: mean anomaly at the ascending node time, ta. )()(tan)cos(tan1aepttEilong +=degrees (6) where: i : inclination angle of the orbit (degrees) p:argument of perigee of the orbit (degrees) : longitude of the ascending node of the orbit (degrees) e: rotati

23、on rate of the Earth (degrees/s) ()sin()sin(sin1Eilatpgeocentric+=degrees (7) The latitude calculated in equation (7) is the geocentric latitude. The geographical latitude can be derived from the geocentric latitude by using the formula in equation (8). ()=)tan(11tan21geocentricalgeographiclatJlat d

24、egrees (8) whereJ is the factor for the Earths oblateness. _ *The solution to this equation has been developed using a trigonometric series developed by Lagrange. 4 Rec. ITU-R S.1593 ()eeREeAltitude = )cos(1 km (9) where: : semi-major axis of the orbit (km) Re: radius of the Earth (km). Step 3 : Det

25、ermine the locations of the other satellite systems that are within the same active arc based on the minimum true anomaly separation and the orbital parameters of the system. The mean anomaly difference between the two satellites that are nearest to their apogee point allows for the computation of t

26、he time intervals between satellite passages over any point in the ground track. For example, if the mean anomaly difference between two satellites is 15 and the orbital period of both satellites is 8 h, then it will take (Em/ 360) T = (15/360) 8 = 1/3 h = 20 min between passages of the two satellit

27、es past any point on the orbit. Since the satellites in the different constellations will follow the same ground tracks, this will allow for the calculation of the location of the satellites in the other constellations at the instant that the first two satellites are nearest to their apogee point (s

28、eparated by the true anomaly separation) by simply adding or subtracting the time interval to the times for the first two satellites. For this example, if one satellite moves forward 20 min in the same orbital ground track, the next satellite (which is in another constellation) will be located at th

29、is point in the orbit when the original satellite is located at one-half the true anomaly separation past apogee. Using the time difference between the first two satellites (these times are calculated in Step 1), the time relative to time of the ascending node for each of the other satellites in the

30、 other systems may be found by simply adding the time difference to the time of the satellite that is past apogee or subtracting the time difference to the time of the satellite that is before apogee. Given the time (relative to the time of the ascending node) of the satellite in the next system, th

31、e mean anomaly, eccentric anomaly, true anomaly, latitude, longitude and altitude of that satellite can be found using the following equations: From the new time, the mean anomaly can be calculated: maamEttTE += )(360degrees (10) The eccentric anomaly is then found by applying an iterative solution

32、to equation (4). The true anomaly is then calculated as: +=eeEEe112tantan21degrees (11) The latitude, longitude and altitude of the satellite at this time can then be calculated using equations (6) through (9). The time interval is added to or subtracted from each new satellite until the time is rea

33、ched where the satellite is not in the active arc. This process results in the locations of all of the satellites in the active arc. Rec. ITU-R S.1593 5 Step 4 : Determine the number of satellites and, thus, systems that are in the active arc. This is a simple process of just adding the number of sa

34、tellites determined in Step 3 to be within the active arc based on the minimum true anomaly separation. In some cases, the satellite entering the active arc and the one leaving the active arc will be of the same system. In these cases, the total number of systems within the active arc will be the to

35、tal number of satellites minus one. Step 5 : Select one satellite to be in the wanted satellite system and calculate the interference from each of the other satellite systems into the wanted system for both the uplink and the downlink and calculate the aggregate interference from all of the interfer

36、ing systems into the wanted system. After selection of the wanted satellite, the earth station location for the wanted system is selected. This selection can be done randomly or a worst-case earth station location can be used. For the uplink, the off-axis angle for the interfering earth station ante

37、nna is calculated (this is the angle between the direction toward the satellite this earth station is communicating with and direction to the wanted satellite). For the downlink, the off-axis angle for the wanted earth station antenna is calculated (this is the angle between the direction toward the

38、 wanted satellite and the direction toward the satellite in the interfering system). The interference contributions from each of the interfering systems into the wanted system are calculated using equation (12) for the uplink and equation (13) for the downlink. ()rsitESESGdfGPI,)log(2045.32)( +=dBW

39、(12) ()()log(2045.32, wrEStssGdfGPI +=dBW (13) where: PES :transmitted power of the interfering earth station (dBW) i : interfering earth station off-axis angle (degrees) GES,t (i): gain of the interfering earth station antenna in the direction of the wanted satellite (dBi) f: frequency of the uplin

40、k (MHz) d: distance between the interfering earth station and the wanted satellite (km) Gs,r: receiving antenna gain of the wanted satellite (dBi) Ps: transmitted power of the interfering satellite (dBW) Gs,t: transmitting antenna gain of the interfering satellite (dBi) f: frequency of the downlink

41、(MHz) 6 Rec. ITU-R S.1593 d: distance between the interfering satellite and the wanted earth station (km) w: wanted earth station off-axis angle (degrees) GES,r(w): gain of the wanted earth station antenna in the direction of the interfering satellite (dBi). The aggregate interference is calculated

42、using equation (14). =nIaggregatenI11010log10 dBW (14) where: n : number of interfering satellite systems In:interference contribution of the n-th system. Step 6 : Calculate the resultant C/(I + N) due to the aggregate interference from these multiple interfering systems for both the uplink and the

43、downlink into the wanted system link budget and calculate the total link C/(I + N). Determine if the system meets its required performance criteria. It is noted that another interference evaluation methodology, such as I/N or T/T may be used in place of C/(I + N). The resultant C/(I + N) for the upl

44、ink and downlink are calculated using equations (15) and (16). +=+10101010log10NIaggregateNI dBW (15) )( NICNIC+=+dB (16) where: N : noise power density and is equal to k T B where: k : Boltzmanns constant T : receiver noise temperature of either the wanted satellite or the wanted earth station (K)

45、B : bandwidth (Hz). The total C/(I + N) for the entire link is calculated using equation (17). +=+101010101010log10 otherNICNICNICtotalNICdB (17) Rec. ITU-R S.1593 7 where: C/(I + N)total:total link C/(I + N) C/(I + N)other: link C/(I + N) due to other sources of interference, such as intermodulatio

46、n, cross polarization and multi-beam. Step 7 : Repeat Steps 5 and 6 for each satellite as the wanted system. Step 8 : If the link budget performance requirements are not met, select a new minimum separation angle and return to Step 2. APPENDIX 1 TO ANNEX 1 Example application of the methodology 1 In

47、troduction This Appendix presents an example application of the methodology described in this Recommen-dation. This example application will use the USAKU-H2 system. 2 Parameters of the USAKU-H2 system used in the analyses The USAKU-H2 system proposes to use sub-geosynchronous inclined elliptical or

48、bits in order to ensure a large angular separation of the active satellites from the GSO orbit. The parameters for the system that are used in this analysis are described below and given in Table 1. More detailed information on this system may be found in Recommendation ITU-R S.1328. The satellites

49、in this system are active only in certain portions of their orbits, and this feature results in active satellite separation angles from the GSO arc of at least 40. The USAKU-H2 system is comprised of three five-satellite sub-constellations two for northern hemisphere operation and one for southern hemisphere operation. The active arcs of th